US9682770B2 - Aircraft landing gear equipped with wheel driving means - Google Patents

Aircraft landing gear equipped with wheel driving means Download PDF

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Publication number
US9682770B2
US9682770B2 US14/640,440 US201514640440A US9682770B2 US 9682770 B2 US9682770 B2 US 9682770B2 US 201514640440 A US201514640440 A US 201514640440A US 9682770 B2 US9682770 B2 US 9682770B2
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rim
wheel
landing gear
actuator
obstacles
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US14/640,440
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US20160176516A1 (en
Inventor
Nicolas MAZARGUIL
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Safran Landing Systems SAS
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Messier Bugatti Dowty SA
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/405—Powered wheels, e.g. for taxing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/80—Energy efficient operational measures, e.g. ground operations or mission management
    • Y02T50/823—

Definitions

  • the invention concerns an aircraft landing gear on which is mounted an actuator for driving a wheel in rotation, said actuator including a lead screw cooperating with obstacles projecting from a lateral face of the rim of the wheel.
  • the driving actuators can be installed easily on the landing gear of different types of aircraft without major integration effort.
  • the mechanical interfaces of the landing gear legs, the wheels and the brakes equipping the wheels can vary greatly between two aircraft of different types.
  • the invention consists in an aircraft landing gear including a driving actuator conforming to the requirements referred to above.
  • an aircraft landing gear including an axle and a wheel that includes a rim mounted to turn on the axle about a first rotation axis, the landing gear further including an actuator for driving the wheel in rotation.
  • the rim includes obstacles that project from a lateral face of the rim and the driving actuator includes a lead screw mounted to turn about a second rotation axis perpendicular to the first rotation axis and adapted to cooperate with the obstacles of the rim to drive the wheel in rotation.
  • the obstacles constitute a toothed ring with which the lead screw of the driving actuator cooperates, said toothed ring being simple to manufacture and relatively light in weight since it consists only of the obstacles and the means for fixing them to the rim.
  • the use of the lead screw makes it possible to obtain a mechanical connection having a high demultiplication ratio. It is therefore possible to reduce the torque that an electric motor of the driving actuator must develop at the same time as increasing the speed of said motor, which makes it possible to reduce the overall size and the mass of said motor of the actuator.
  • FIG. 1 is a perspective view of landing gear in accordance with the invention bearing two wheels each adapted to be driven in rotation by a driving actuator, the driving actuators being in a meshing position, the tire of one of these two wheels having been omitted for clarity;
  • FIG. 2 is a front view of landing gear analogous to that from FIG. 1 ;
  • FIG. 3 is a sectional view of the landing gear in accordance with the invention on a section plane parallel to the lateral faces of the wheels of the landing gear and passing through the center of a leg of the landing gear;
  • FIG. 4 a is a perspective view from above of driving means including first and second driving actuators, a meshing actuator and an actuator support, the driving actuators being in a release position;
  • FIG. 4 b is a view analogous to that of FIG. 4 a in which the driving actuators are in a meshing position;
  • FIG. 5 a is a view from below analogous to that of FIG. 4 a;
  • FIG. 5 b is a view from below analogous to that of FIG. 4 b;
  • FIG. 6 a is a rear view analogous to that of FIG. 4 a;
  • FIG. 6 b is a rear view analogous to that of FIG. 4 b;
  • FIGS. 7 a and 7 b represent one of the obstacles with which the lead screw of a driving actuator cooperates in a first embodiment of the invention
  • FIG. 8 represents an obstacle in accordance with a second embodiment of the invention.
  • the landing gear 1 in accordance with a first embodiment of the invention here includes in the conventional way a strut assembly 2 articulated to the structure of an aircraft in which a sliding rod 3 is mounted to slide telescopically.
  • the sliding rod 3 represented here in an entirely retracted position, carries at its end an axle 4 supporting a first wheel 5 a and a second wheel 5 b .
  • a compass arm 10 connects the strut assembly 2 and the sliding rod 3 to ensure sliding without rotation of the sliding rod 3 .
  • Each wheel 5 a , 5 b includes a rim 6 that carries a tire 7 and that is mounted to turn on the axle 4 about an axis of the axle 4 or first rotation axis X 1 by means of bearings.
  • Each wheel 5 a , 5 b is furthermore equipped with a brake adapted to brake the wheel, the brake including a stack of carbon disks inside the rim 6 of the wheel and not visible in the figures, a ring 9 fixed to the axle 4 , and a plurality of electromechanical actuators 11 carried by the ring 9 and adapted selectively to apply a braking force to the stack of disks.
  • the landing gear 1 of the invention furthermore includes means for driving the wheels 5 a , 5 b of the aircraft in rotation, said driving means including a first actuator 12 a for driving the first wheel 5 a in rotation, a second actuator 12 b for driving the second wheel 5 b in rotation, a meshing actuator 13 , and an actuator support 15 mounted on the sliding rod 3 of the landing gear 1 and carrying the first and second driving actuators 12 a , 12 b and the meshing actuator 13 .
  • the actuator support 15 is fixed to a rear compass arm axle 17 itself fastened to the sliding rod 3 and to a spherical head 18 of the sliding rod 3 via a tubular centring stud 19 (seen better in FIGS. 6 a and 6 b ) that extends inside the sliding rod 3 through a bore 21 provided in the latter.
  • the first and second driving actuators 12 a , 12 b are each mounted to pivot on the actuator support 15 about parallel first pivot axes Xp 1 situated on either side of the actuator support 15 so as to move toward or away from the rim 6 of the first wheel 5 a and the rim 6 of the second wheel 5 b , respectively.
  • the meshing actuator 13 includes an electric motor, an actuating member 23 , a first arm 24 a and a second arm 24 b .
  • the electric motor of the meshing actuator 13 is adapted to move the actuating member 23 selectively away from or toward the actuating member 23 of the actuator support 15 in a linear movement represented by the double-headed arrow 25 in FIG. 2 .
  • the first and second arms 24 a , 24 b are each mounted to pivot at one of their ends on the actuating member 23 about second pivot axes Xp 2 and at the other of their ends on the first and second driving actuators 12 a , 12 b , respectively, about third pivot axes Xp 3 situated on the first and second driving actuators 12 a , 12 b (the pivot axes Xp 2 and Xp 3 can be seen in FIG. 2 ).
  • the second pivot axes Xp 2 and the third pivot axes Xp 3 are all parallel to the first pivot axes Xp 1 .
  • movement of the actuating member 23 away from the actuator support 15 simultaneously moves the first and second driving actuators 12 a , 12 b toward the rims 6 of the first and second wheels 5 a , 5 b
  • movement of the actuating member 23 toward the actuator support 15 simultaneously moves the first and second driving actuators 12 a , 12 b away from the rims 6 of the first and second wheels 5 a , 5 b.
  • the meshing actuator 13 is thus adapted to move the driving actuators 12 simultaneously between a meshing position, in which they are positioned to drive the wheels 5 a , 5 b in rotation, and a release position, in which they are away from the wheels 5 a , 5 b and allow the latter to rotate freely.
  • the operation of the driving actuators 12 and the manner in which they cooperate with the wheels 5 a , 5 b to drive them in rotation when they are in the meshing position are described in more detail next.
  • the first and second actuators 12 a , 12 b function in the same manner, their operation will be described with reference to only one driving actuator 12 and one wheel.
  • the driving actuator 12 includes an actuator body 27 , an electric motor 28 represented diagrammatically and positioned in the actuator body 27 , a gearbox 29 , and a transmission shaft 31 and a lead screw 32 connected to the transmission shaft 31 .
  • the transmission shaft 31 and the lead screw 32 extend outside the actuator body 27 .
  • the electric motor 28 of the driving actuator 12 is adapted to drive the transmission shaft 31 and therefore the lead screw 32 in rotation via the gearbox 29 about a second rotation axis X 2 perpendicular to the axis of the axle or first rotation axis X 1 .
  • the rim 6 of the wheel includes obstacles 33 that project from a lateral face F of the rim 6 facing the associated driving actuator 12 .
  • These obstacles 33 are removable rollers 33 attached to a support ring 34 fixed to the circumference of the lateral face F of the rim 6 .
  • Each roller 33 includes a smooth first hole 35 extending through the roller 33 from one side to the other.
  • the smooth first hole 35 is extended by a threaded second hole 36 in the support ring 34 .
  • the roller 33 is fixed to the support ring 34 by a bolt extending through the smooth first hole 35 and into the threaded second hole 36 .
  • rollers 33 are parts subject to wear, intended to be replaced at a predetermined frequency, for example at a frequency equal to that of replacing the tires 7 of the wheels.
  • the lead screw 32 cooperates with the rollers 33 to drive the wheel in rotation. Note that, depending on the direction of rotation of the electric motor 28 and therefore the direction of rotation of the lead screw 32 , the wheel 5 a , 5 b is driven in rotation in a direction tending either to move the aircraft forward or to move the aircraft backward.
  • the lead screw 32 of the driving actuator 12 here includes two threads 38 (visible in FIG. 1 ): this increases the demultiplication ratio of the connection between the lead screw 32 and the rollers 33 and reduces the stresses applied to each thread 38 of said lead screw 32 .
  • the threads 38 have a helix angle sufficiently large, given the coefficient of friction of the connection between the lead screw 32 and the rollers 33 , to render this connection reversible.
  • the actuator 12 is provided with a clutch device between the gearbox 29 and the lead screw 32 .
  • This clutch device makes it possible to uncouple the lead screw 32 from the gearbox 29 , to facilitate meshing of the lead screw 32 and the rollers 33 when the driving actuator 12 comes into the meshing position when the wheel of the aircraft is already rotating at a non-zero speed.
  • each roller 39 includes here a base 41 forming a fixed interior race of a ball bearing, an upper part 42 forming an exterior race of the ball bearing, and balls 43 disposed on a raceway of the exterior race.
  • the upper part 42 of each roller 39 includes a first threaded hole 44 .
  • the base 41 includes a second threaded hole 45 passing through the base 41 from one side to the other and extending the first threaded hole 44 .
  • the first and second threaded holes 44 , 45 are extended by a third threaded hole 46 in the support ring 34 .
  • the roller 39 is fixed to the support ring 34 by a bolt extending through the first and second threaded holes 44 , 45 and into the third threaded hole 46 .
  • lead screws are provided with two threads
  • the invention applies to lead screws provided with at least one thread.
  • the rollers are mounted on the lateral face of the rim by being attached to an intermediate support, in this instance to a support ring itself fixed to the lateral surface of the rim of the wheel, it is perfectly possible to attach the rollers directly to the lateral face of the rim or to use an intermediate support of different shape.
  • the invention of course applies to landing gear equipped with wheels not provided with brakes, such as an aircraft auxiliary landing gear.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transmission Devices (AREA)
  • Braking Arrangements (AREA)
US14/640,440 2014-03-12 2015-03-06 Aircraft landing gear equipped with wheel driving means Active 2035-03-14 US9682770B2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1452063 2014-03-12
FR1452063A FR3018502B1 (fr) 2014-03-12 2014-03-12 Atterrisseur d'aeronef

Publications (2)

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US20160176516A1 US20160176516A1 (en) 2016-06-23
US9682770B2 true US9682770B2 (en) 2017-06-20

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US14/640,440 Active 2035-03-14 US9682770B2 (en) 2014-03-12 2015-03-06 Aircraft landing gear equipped with wheel driving means

Country Status (4)

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US (1) US9682770B2 (fr)
EP (1) EP2918494B1 (fr)
CN (1) CN104908930B (fr)
FR (1) FR3018502B1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3022216B1 (fr) * 2014-06-13 2018-01-26 Safran Landing Systems Roue d'aeronef equipee de moyens de son entrainement en rotation par un actionneur d'entrainement.
FR3048954B1 (fr) * 2016-03-21 2019-08-23 Safran Landing Systems Systeme de desengagement verrouillable d’actionneur de roue sur un atterisseur d’aeronef.

Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1359566A (en) * 1920-03-17 1920-11-23 Bender Berlin Flying-machine
US1812143A (en) * 1930-03-22 1931-06-30 Robert B Davis Airplane
US2287491A (en) * 1940-09-19 1942-06-23 Percy B Wolverton Aircraft landing gear
US2320547A (en) * 1942-01-30 1943-06-01 Roy L Tiger Landing wheel rotating device for airplanes
US2404018A (en) * 1944-03-23 1946-07-16 Bernard E Yaggy Airplane landing gear
US2425583A (en) * 1945-06-15 1947-08-12 Curtiss Wright Corp Wheel rotating mechanism
US2460387A (en) * 1943-12-03 1949-02-01 Goodrich Co B F Landing gear
US3059712A (en) * 1961-11-13 1962-10-23 Charles F Hautau Aircraft wheel powering device
US3428274A (en) * 1966-09-19 1969-02-18 Wally Ellis Aircraft touchdown wheel synchronizer
US3542318A (en) * 1968-09-09 1970-11-24 Ralph G Ellsworth Apparatus for rotating aircraft wheels prior to landing
US3814354A (en) * 1973-05-14 1974-06-04 Oldrich Drake Landing wheel rotating device for aircraft
US3850389A (en) * 1973-05-04 1974-11-26 D Dixon Landing gear wheel device for aircraft
US3919899A (en) * 1973-12-05 1975-11-18 Parker Bruce H Jun Self aligning planetary gear differential
US20130026284A1 (en) * 2011-07-27 2013-01-31 Honeywell International Inc. Aircraft taxi system including drive chain
EP2581305A1 (fr) 2011-10-14 2013-04-17 Messier-Bugatti-Dowty Dispositif de connexion d'un motoréducteur à une roue d'aéronef, pour permettre son entraînement sélectif par le motoréducteur.
US20130200210A1 (en) * 2010-04-28 2013-08-08 L-3 Communications Magnet-Motor Gmbh Drive unit for aircraft running gear
US20130233969A1 (en) * 2012-03-12 2013-09-12 Honeywell International Inc. Movable bushing interface and taxi drive system
US8646722B2 (en) * 2010-01-26 2014-02-11 Airbus Operations Limited Aircraft taxiing actuator
US20140225421A1 (en) * 2011-06-17 2014-08-14 L-3 Communication Magnet-Motor GMBH Drive unit for aircraft running gear wheels
US20150210384A1 (en) * 2014-01-24 2015-07-30 Honeywell International Inc. Aircraft wheel driving system
US9211948B2 (en) * 2013-03-24 2015-12-15 Honeywell International Inc. Between-wheel bogie mounted taxi system

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2874675B1 (fr) * 2004-08-26 2006-12-08 Messier Bugatti Sa Frein pour roue avec capteur d'usure
FR2954752B1 (fr) * 2009-12-24 2012-03-09 Messier Bugatti Ensemble de roue et frein pour aeronef equipe d'un dispositif d'entrainement en rotation.
FR2968274B1 (fr) * 2010-12-06 2013-02-01 Messier Bugatti Dispositif de freinage/entrainement d'une roue d'aeronef.

Patent Citations (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1359566A (en) * 1920-03-17 1920-11-23 Bender Berlin Flying-machine
US1812143A (en) * 1930-03-22 1931-06-30 Robert B Davis Airplane
US2287491A (en) * 1940-09-19 1942-06-23 Percy B Wolverton Aircraft landing gear
US2320547A (en) * 1942-01-30 1943-06-01 Roy L Tiger Landing wheel rotating device for airplanes
US2460387A (en) * 1943-12-03 1949-02-01 Goodrich Co B F Landing gear
US2404018A (en) * 1944-03-23 1946-07-16 Bernard E Yaggy Airplane landing gear
US2425583A (en) * 1945-06-15 1947-08-12 Curtiss Wright Corp Wheel rotating mechanism
US3059712A (en) * 1961-11-13 1962-10-23 Charles F Hautau Aircraft wheel powering device
US3428274A (en) * 1966-09-19 1969-02-18 Wally Ellis Aircraft touchdown wheel synchronizer
US3542318A (en) * 1968-09-09 1970-11-24 Ralph G Ellsworth Apparatus for rotating aircraft wheels prior to landing
US3850389A (en) * 1973-05-04 1974-11-26 D Dixon Landing gear wheel device for aircraft
US3814354A (en) * 1973-05-14 1974-06-04 Oldrich Drake Landing wheel rotating device for aircraft
US3919899A (en) * 1973-12-05 1975-11-18 Parker Bruce H Jun Self aligning planetary gear differential
US8646722B2 (en) * 2010-01-26 2014-02-11 Airbus Operations Limited Aircraft taxiing actuator
US20130200210A1 (en) * 2010-04-28 2013-08-08 L-3 Communications Magnet-Motor Gmbh Drive unit for aircraft running gear
US20140225421A1 (en) * 2011-06-17 2014-08-14 L-3 Communication Magnet-Motor GMBH Drive unit for aircraft running gear wheels
US20130026284A1 (en) * 2011-07-27 2013-01-31 Honeywell International Inc. Aircraft taxi system including drive chain
EP2581305A1 (fr) 2011-10-14 2013-04-17 Messier-Bugatti-Dowty Dispositif de connexion d'un motoréducteur à une roue d'aéronef, pour permettre son entraînement sélectif par le motoréducteur.
US20130233969A1 (en) * 2012-03-12 2013-09-12 Honeywell International Inc. Movable bushing interface and taxi drive system
US9211948B2 (en) * 2013-03-24 2015-12-15 Honeywell International Inc. Between-wheel bogie mounted taxi system
US20150210384A1 (en) * 2014-01-24 2015-07-30 Honeywell International Inc. Aircraft wheel driving system

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Title
Black, Aaron; The Ins and Outs of Worm Gears; <http://machinerylubrication.com/Read/1080/worm-gears>; Nov. 16, 2012 via archive.org. *
French Search Report for FR 14 52063 dated Dec. 1, 2014.
Written Opinion for FR 14 52063 dated Mar. 12, 2014.

Also Published As

Publication number Publication date
CN104908930B (zh) 2018-01-05
FR3018502B1 (fr) 2018-03-23
EP2918494A1 (fr) 2015-09-16
EP2918494B1 (fr) 2018-12-05
CN104908930A (zh) 2015-09-16
US20160176516A1 (en) 2016-06-23
FR3018502A1 (fr) 2015-09-18

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